EP3126920A2 - System and method for heatlh monitoring of servo-hydraulic actuators - Google Patents
System and method for heatlh monitoring of servo-hydraulic actuatorsInfo
- Publication number
- EP3126920A2 EP3126920A2 EP15772524.3A EP15772524A EP3126920A2 EP 3126920 A2 EP3126920 A2 EP 3126920A2 EP 15772524 A EP15772524 A EP 15772524A EP 3126920 A2 EP3126920 A2 EP 3126920A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- hydraulic fluid
- leakage
- cylinder
- pressure
- piston
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
- 238000000034 method Methods 0.000 title claims abstract description 30
- 238000012544 monitoring process Methods 0.000 title claims abstract description 10
- 239000012530 fluid Substances 0.000 claims abstract description 108
- 230000036541 health Effects 0.000 claims abstract description 34
- 230000004044 response Effects 0.000 claims abstract description 27
- 230000015556 catabolic process Effects 0.000 claims description 16
- 238000006731 degradation reaction Methods 0.000 claims description 16
- 238000001514 detection method Methods 0.000 claims description 7
- 230000004931 aggregating effect Effects 0.000 claims 2
- 238000012423 maintenance Methods 0.000 description 5
- 238000013459 approach Methods 0.000 description 4
- 230000007246 mechanism Effects 0.000 description 3
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
- 230000005540 biological transmission Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000002955 isolation Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000009529 body temperature measurement Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 238000007499 fusion processing Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000011179 visual inspection Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B19/00—Testing; Calibrating; Fault detection or monitoring; Simulation or modelling of fluid-pressure systems or apparatus not otherwise provided for
- F15B19/005—Fault detection or monitoring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B20/00—Safety arrangements for fluid actuator systems; Applications of safety devices in fluid actuator systems; Emergency measures for fluid actuator systems
- F15B20/005—Leakage; Spillage; Hose burst
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F23/00—Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F25/00—Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume
- G01F25/20—Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume of apparatus for measuring liquid level
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/002—Investigating fluid-tightness of structures by using thermal means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/26—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
- G01M3/28—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors for pipes, cables or tubes; for pipe joints or seals; for valves ; for welds
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/26—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
- G01M3/32—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors for containers, e.g. radiators
- G01M3/3236—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors for containers, e.g. radiators by monitoring the interior space of the containers
- G01M3/3245—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors for containers, e.g. radiators by monitoring the interior space of the containers using a level monitoring device
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0259—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the response to fault detection
- G05B23/0283—Predictive maintenance, e.g. involving the monitoring of a system and, based on the monitoring results, taking decisions on the maintenance schedule of the monitored system; Estimating remaining useful life [RUL]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B2211/00—Circuits for servomotor systems
- F15B2211/60—Circuit components or control therefor
- F15B2211/63—Electronic controllers
- F15B2211/6303—Electronic controllers using input signals
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B2211/00—Circuits for servomotor systems
- F15B2211/60—Circuit components or control therefor
- F15B2211/63—Electronic controllers
- F15B2211/6303—Electronic controllers using input signals
- F15B2211/6306—Electronic controllers using input signals representing a pressure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
- F15B2211/00—Circuits for servomotor systems
- F15B2211/60—Circuit components or control therefor
- F15B2211/63—Electronic controllers
- F15B2211/6303—Electronic controllers using input signals
- F15B2211/6343—Electronic controllers using input signals representing a temperature
Definitions
- the subject matter disclosed herein generally relates to health monitoring of aircraft. More specifically, the subject disclosure relates to health assessment of hydraulic systems of an aircraft.
- a leading driver of maintenance for hydraulic flight control systems is fluid leakage. This includes both external leakage that drains fluid from the stored supply, and internal leakage that reduces component efficiency and degrades system response.
- Current generation aircraft generally include a Leak Detection and Isolation (LDI) system that is targeted at severe leak conditions that compromise system safety. Generally speaking if the LDI system can observe the leak, enough fluid has been lost that the affected components or system lines need to be isolated by valves and backup systems engaged as required to restore aircraft control. Also, this system provides no information about internal leak conditions that may seriously degrade system performance.
- LKI Leak Detection and Isolation
- a method of health monitoring of a hydraulic actuator includes sensing a first hydraulic fluid pressure at a first chamber of a hydraulic cylinder, the first chamber defined by a piston disposed in the cylinder and a first cylinder wall. The method further includes sensing a second hydraulic fluid pressure at a second chamber of the hydraulic cylinder, the second chamber defined by the piston and a second cylinder wall opposite the first cylinder wall. The pressures are summed to derive a pressure sum leakage estimate. An actual piston position in the hydraulic cylinder is determined and compared to an intended piston position to determine a positional error of the piston. A command- response error leakage estimate is derived from the positional error. The pressure sum leakage estimate and the command-response error leakage estimate are fused to determine an internal hydraulic fluid leakage in the hydraulic cylinder.
- a pressure difference is calculated from the sensed first hydraulic fluid pressure and the second hydraulic fluid pressure, and a hydraulic fluid temperature is detected.
- the pressure sum leakage estimate and/or the command-response error leakage estimate are compensated based on the pressure difference and/or the hydraulic fluid temperature.
- an actuator health indicator is derived from the internal hydraulic fluid leakage.
- actuator health indicators of a plurality of actuators are aggregated into a system health indicator.
- the internal hydraulic fluid leakage is compared to one or more previously determined internal hydraulic fluid leakages, and a degradation rate is determined based on the comparison.
- an actuator health indicator is derived from the internal hydraulic fluid leakage and the degradation rate.
- the positional errors of the piston are determined at a same intended piston position.
- a method of health monitoring of a hydraulic actuator includes sensing a first hydraulic fluid pressure at a first chamber of a hydraulic cylinder, the first chamber defined by a piston disposed in the cylinder and a first cylinder wall and sensing a second hydraulic fluid pressure at a second chamber of the hydraulic cylinder, the second chamber defined by the piston and a second cylinder wall opposite the first cylinder wall.
- the first hydraulic fluid pressure and the second hydraulic fluid pressure are summed to derive a pressure sum leakage, indicative of internal hydraulic fluid leakage in the hydraulic cylinder.
- an actual piston position in the hydraulic cylinder is determined.
- the actual piston position is compared to an intended piston position to determine a positional error of the piston.
- a command-response error leakage estimate is derived from the positional error and the pressure sum leakage estimate and the command-response error leakage estimate are fused to determine the internal hydraulic fluid leakage in the hydraulic cylinder.
- a pressure difference is calculated from the measured first hydraulic fluid pressure and the second hydraulic fluid pressure and a hydraulic fluid temperature is detected.
- the pressure sum leakage estimate is compensated based on the pressure difference and/or the hydraulic fluid temperature.
- an actuator health indicator is derived from the internal hydraulic fluid leakage.
- actuator health indicators of a plurality of actuators are aggregated into a system health indicator.
- the internal hydraulic fluid leakage is compared to one or more previously determined internal hydraulic fluid leakages, and a degradation rate is determined based on the comparison.
- an actuator health indicator is derived from the internal hydraulic fluid leakage and the degradation rate.
- a method of health monitoring of a hydraulic actuator includes determining an actual piston position of a piston in a hydraulic cylinder of the hydraulic actuator and comparing the actual piston position to an intended piston position to determine a positional error of the piston.
- a command-response error leakage estimate is derived from the positional error, indicative of an internal hydraulic fluid leakage in the hydraulic cylinder.
- a first hydraulic fluid pressure is sensed at a first chamber of a hydraulic cylinder, the first chamber defined by the piston and a first cylinder wall and a second hydraulic fluid pressure is sensed at a second chamber of the hydraulic cylinder, the second chamber defined by the piston and a second cylinder wall opposite the first cylinder wall.
- the first hydraulic fluid pressure and the second hydraulic fluid pressure are summed to derive a pressure sum leakage estimate.
- the pressure sum leakage estimate and the command-response error leakage estimate are fused to determine the internal hydraulic fluid leakage in the hydraulic cylinder.
- a pressure difference is calculated from the measured first hydraulic fluid pressure and the second hydraulic fluid pressure, and a hydraulic fluid temperature is detected.
- the pressure sum leakage estimate and/or the command-response error leakage estimate is compensated based on the pressure difference and/or the hydraulic fluid temperature.
- an actuator health indicator is derived from the internal hydraulic fluid leakage.
- the internal hydraulic fluid leakage is compared to one or more previously determined internal hydraulic fluid leakages and a degradation rate based on the comparison.
- An actuator health indicator is derived from the internal hydraulic fluid leakage and the degradation rate.
- a hydraulic actuator system includes a cylinder and a piston positioned in the cylinder defining a first cylinder chamber and a second cylinder chamber, the piston operably connected to a piston shaft.
- a leakage detection system is operably connected to the cylinder and includes one or more pressure sensors to detect a first hydraulic fluid pressure in the first chamber and a second hydraulic fluid pressure in the second chamber.
- the leakage detection system is configured to sum the first hydraulic fluid pressure and the second hydraulic fluid pressure to derive a pressure sum leakage estimate, determine an actual piston position in the hydraulic cylinder, compare the actual piston position to an intended piston position to determine a positional error of the piston, derive a command-response error leakage estimate from the positional error, and fuse the pressure sum leakage estimate and the command-response error leakage estimate to determine an internal hydraulic fluid leakage in the hydraulic cylinder.
- FIG. 1 is an illustration of an embodiment of an aircraft
- FIG. 2 is an illustration of an embodiment of a hydraulic actuator for an aircraft.
- FIG. 3 is a schematic illustration of a leak detection system for a hydraulic actuator.
- FIG. 1 illustrates an exemplary rotary- winged aircraft 10 having a main rotor system 12, which rotates about a rotor axis 14.
- the aircraft 10 includes an airframe 16 which supports the main rotor system 12 as well as an extending tail 18 including a tail rotor 20.
- the main rotor system 12 includes a plurality of rotor blade assemblies 22 mounted to a rotor hub assembly 24.
- the main rotor system 12 is driven by a transmission 26.
- the transmission 26 includes a main gearbox 28 driven by one or more engines, illustrated schematically at 30.
- the main gearbox 28 and engines 30 are considered as part of the non-rotating frame of the aircraft 10.
- the main gearbox 28 may be interposed between one or more gas turbine engines 30 and the main rotor system 12.
- gas turbine engines 30 may be interposed between one or more gas turbine engines 30 and the main rotor system 12.
- a particular rotary wing aircraft configuration is illustrated and described in the disclosed non- limiting embodiment, other configurations and/or machines with rotor systems are within the scope of the present invention.
- the present disclosure may be utilized in other, non-rotary winged aircraft applications. It is to be appreciated that while the description herein relates to a rotary wing aircraft, the disclosure herein may be as readily applied to fixed wing aircraft, ground vehicles, industrial machinery, or other applications that use servo-hydraulic actuators.
- the aircraft 10 may include many systems, such as rotor blade pitch adjustment, ailerons, landing gear and/or other systems, driven by servo-hydraulic actuators 32, an example of which is illustrated in FIG. 2.
- the actuator 32 includes a cylinder 34 having a piston 36 located in the cylinder 34, which separates the cylinder 34 into a first chamber 38 and a second chamber 40.
- the piston 36 includes a piston shaft 42 to transmit force outside of the cylinder 34.
- the piston shaft 42 is connected to a control surface (not shown) of the like, such that movement of the piston shaft 42 along a piston axis 44 effects movement of the control surface.
- This control surface is under external load 70 from a combination of aerodynamic forces, friction, inertia, and any other system forces.
- Movement of the piston shaft 42 and the piston 36 is driven by differential fluid pressure between the first chamber 38 and the second chamber 40 when compared to the external actuator load 70.
- the piston 36 is driven from a first chamber wall 46 toward a second chamber wall 48. This continues until the force due to the delta pressure acting on the piston area is balanced with external load 70, effectively enlarging the first chamber 38 and decreasing a volume of the second chamber 40.
- the first chamber 38 and the second chamber 40 include first port 50 and second port 52, respectively, which serve as inlet and outlet for hydraulic fluid 54.
- the flow of hydraulic fluid 54 through the first port 50 and second port 52 is controlled by a servo- valve mechanism 56 operably connected to a hydraulic fluid source (not shown) at supply port 72. Fluid is drained to the hydraulic return through return port 74.
- the servo-valve mechanism 56 may be electronically controlled or positioned by direct mechanical input.
- the piston 36 includes one or more piston seals 58 located at an outer periphery of the piston 36 to seal between the piston 36 and a cylinder wall 60.
- the piston seals 58 are configured to prevent leakage of hydraulic fluid 54 around the piston between the first chamber 38 and the second chamber 40. Over time, however, the piston seals 58 lose effectiveness through, for example, degradation of or damage to the piston seals 58 or degradation of or damage to the cylinder wall 60. This alters the fluid pressures in the first chamber 38 and the second chamber 40, resulting in reduced performance of the actuator 32, and in some cases failure.
- a leak detection system 62 To detect such leakage before failure of the actuator 32, a leak detection system 62, schematically shown in FIG. 3, is utilized. Pressure sensors 66 (shown in FIG. 2) detect hydraulic fluid 54 pressure at the first chamber 38 and the second chamber 40 in block 68. These pressures are combined to calculate a pressure sum in 76, and are differenced to provide a delta pressure at block 78. A hydraulic fluid temperature is detected by one or more temperature sensors 64 that may be located in various locations in the actuator 32, for example, in either chamber 38, 40 or in the servo supply line 72 or return line 74. The calculated delta pressure 78 and fluid temperature measurement 80 are utilized in combination with a model to perform temperature and load compensation at block 82 and produce a leak size estimate that is independent of these factors at block 84.
- a position comparison is performed between a piston actual position 88 derived from, for example, a position sensor 108, and a piston intended position 90 derived from the servo mechanism 56, fly-by-wire device or other actuator controller.
- the result of the position comparison is a positional error 86 and is indicative of piston seal 58 leakage, where a relatively small positional error 86 indicates little or no leakage and a relatively large positional error 86 indicates a greater amount of leakage.
- the position error 86 is also influenced by the operating temperature and external load.
- a model 92 is used to compensate for these effects using observations of the delta pressure 78 and the fluid temperature 80, resulting in a corrected command-response leakage estimate 94.
- a weighted data fusion process 96 combines the multiple leak estimates 84, 94 into a single estimated fault size 98 and, when appropriate, triggers a diagnostic flag 100 indicating maintenance attention is needed.
- the estimated fault size 98 can represent, for example, internal hydraulic fluid leakage.
- pressure sum and command response error changes may be compared to previously determined values at the data fusion algorithm 96 to arrive at a degradation rate 102.
- the past and current observations of compensated pressure sum 84 and the command-response leakage estimate 94 are combined with the degradation rate 102 information using weight factors that give priority to either approach based upon defined confidence metrics for the respective approaches for various leak sizes and operating conditions.
- the fused assessment of internal leakage is used to derive a health indicator 104, which in some embodiments is rolled up into a formulation of an aircraft or system health indicator 106, including actuator health indicators 104 from other actuators 32 in the system or other hydraulic components like pumps, valves, or fluid lines.
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Automation & Control Theory (AREA)
- Fluid-Pressure Circuits (AREA)
- Examining Or Testing Airtightness (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201461974025P | 2014-04-02 | 2014-04-02 | |
PCT/US2015/023819 WO2015153727A2 (en) | 2014-04-02 | 2015-04-01 | System and method for heatlh monitoring of servo-hydraulic actuators |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3126920A2 true EP3126920A2 (en) | 2017-02-08 |
EP3126920A4 EP3126920A4 (en) | 2018-01-03 |
Family
ID=54241248
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15772524.3A Withdrawn EP3126920A4 (en) | 2014-04-02 | 2015-04-01 | System and method for heatlh monitoring of servo-hydraulic actuators |
EP15773167.0A Withdrawn EP3126807A4 (en) | 2014-04-02 | 2015-04-01 | System and method for health monitoring of hydraulic systems |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15773167.0A Withdrawn EP3126807A4 (en) | 2014-04-02 | 2015-04-01 | System and method for health monitoring of hydraulic systems |
Country Status (3)
Country | Link |
---|---|
US (2) | US20170211600A1 (en) |
EP (2) | EP3126920A4 (en) |
WO (2) | WO2015153731A1 (en) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3056650B1 (en) * | 2016-09-27 | 2019-06-14 | Airbus Helicopters | METHOD FOR DETECTING LEAKAGE OF SERVOCOMMAND, AND ASSOCIATED AIRCRAFT |
US10775211B2 (en) * | 2017-05-03 | 2020-09-15 | Quest Automated Services, LLC | Real-time vessel monitoring system |
FR3072475B1 (en) * | 2017-10-17 | 2019-11-01 | Thales | METHOD OF PROCESSING AN ERROR DURING THE EXECUTION OF A PREDETERMINED AVIONIC PROCEDURE, COMPUTER PROGRAM AND SYSTEM FOR DETECTION AND ALERT |
GB2571100A (en) * | 2018-02-15 | 2019-08-21 | Airbus Operations Ltd | Controller for an aircraft braking system |
US10837472B2 (en) * | 2018-02-22 | 2020-11-17 | Caterpillar Inc. | Hydraulic cylinder health monitoring and remaining life system |
CN108843654A (en) * | 2018-07-04 | 2018-11-20 | 上海交通大学 | A kind of valve control cylinder mode leakage judgment means and method based on Subspace Identification |
US11143328B2 (en) | 2019-03-06 | 2021-10-12 | Honeywell International Inc. | Health monitoring for proportional actuators |
US11193810B2 (en) | 2020-01-31 | 2021-12-07 | Pratt & Whitney Canada Corp. | Validation of fluid level sensors |
CN113418663B (en) * | 2020-12-31 | 2024-05-03 | 湖南江河机电自动化设备股份有限公司 | Leakage detection method for hydraulic system of hydraulic turbine governor |
US20220243746A1 (en) * | 2021-02-01 | 2022-08-04 | The Heil Co. | Hydraulic cylinder monitoring |
EP4098889B1 (en) | 2021-06-02 | 2023-09-20 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A failure detection apparatus for a hydraulic system |
US20240125674A1 (en) * | 2022-10-14 | 2024-04-18 | The Boeing Company | Diagnostic system and method for monitoring hydraulic pump |
Family Cites Families (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS6155405A (en) * | 1984-08-28 | 1986-03-19 | Hitachi Constr Mach Co Ltd | Internal leakage detecting system for hydraulic cylinder |
US4835522A (en) * | 1987-11-05 | 1989-05-30 | Emhart Industries, Inc. | Tank inventory and leak detection system |
US5201212A (en) * | 1991-02-13 | 1993-04-13 | Tanknology Corporation International | Line leak detector and method |
US5402110A (en) * | 1994-02-03 | 1995-03-28 | Ransomes America Corporation | Hydraulic fluid leak detection system and method |
US5883815A (en) * | 1996-06-20 | 1999-03-16 | Drakulich; Dushan | Leak detection system |
US7043975B2 (en) * | 2003-07-28 | 2006-05-16 | Caterpillar Inc | Hydraulic system health indicator |
DE10355250B4 (en) * | 2003-11-26 | 2005-09-01 | Festo Ag & Co. | Method for determining leaks of a pressure fluid in a pressure actuated machine using a mathematical equation relating pressure and flow volume and comparing actual values to a reference value |
US7347083B2 (en) * | 2005-08-04 | 2008-03-25 | The Boeing Company | System and method for detecting a leak in a hydraulic fluid system |
DE102006011807A1 (en) * | 2006-03-15 | 2007-09-20 | Zf Friedrichshafen Ag | Method for fault detection on an actuator |
US7353691B2 (en) * | 2006-06-02 | 2008-04-08 | General Electric Company | High performance generator stator leak monitoring system |
ATE466192T1 (en) * | 2007-05-04 | 2010-05-15 | Saab Ab | ARRANGEMENT AND METHOD FOR MONITORING A HYDRAULIC SYSTEM |
NO329732B1 (en) * | 2007-08-21 | 2010-12-13 | Nat Oilwell Varco Norway As | A method for detecting a fluid leakage by a piston machine |
FR2922521A1 (en) * | 2007-10-23 | 2009-04-24 | Airbus France Sas | HYDRAULIC SYSTEM FOR AIRCRAFT. |
US7970583B2 (en) * | 2007-12-28 | 2011-06-28 | United Technologies Corporation | Degraded actuator detection |
ES2411385T3 (en) * | 2009-06-22 | 2013-07-05 | Siemens Aktiengesellschaft | Leak detection system in a wind turbine |
US20110112814A1 (en) * | 2009-11-11 | 2011-05-12 | Emerson Retail Services, Inc. | Refrigerant leak detection system and method |
DE102010015636A1 (en) * | 2010-04-20 | 2011-10-20 | Airbus Operations Gmbh | Device and a method for determining the aging state of a hydraulic fluid of a hydraulic system of a vehicle |
US8600566B1 (en) * | 2011-02-04 | 2013-12-03 | The United States Of America As Represented By The Secretary Of The Navy | Thermal management smart valve with rupture detection and isolation |
US20130073190A1 (en) * | 2011-09-21 | 2013-03-21 | Honda Motor Co., Ltd. | Engine Start Up Control For A Motor Vehicle |
US8683860B2 (en) * | 2011-10-28 | 2014-04-01 | The Boeing Company | Flow-gain based hydraulic actuator leakage test |
US9128008B2 (en) * | 2012-04-20 | 2015-09-08 | Kent Tabor | Actuator predictive system |
-
2015
- 2015-04-01 US US15/300,664 patent/US20170211600A1/en not_active Abandoned
- 2015-04-01 EP EP15772524.3A patent/EP3126920A4/en not_active Withdrawn
- 2015-04-01 EP EP15773167.0A patent/EP3126807A4/en not_active Withdrawn
- 2015-04-01 WO PCT/US2015/023830 patent/WO2015153731A1/en active Application Filing
- 2015-04-01 US US15/300,681 patent/US20170184138A1/en not_active Abandoned
- 2015-04-01 WO PCT/US2015/023819 patent/WO2015153727A2/en active Application Filing
Also Published As
Publication number | Publication date |
---|---|
US20170184138A1 (en) | 2017-06-29 |
WO2015153727A2 (en) | 2015-10-08 |
EP3126807A4 (en) | 2017-11-22 |
US20170211600A1 (en) | 2017-07-27 |
WO2015153731A1 (en) | 2015-10-08 |
EP3126807A1 (en) | 2017-02-08 |
EP3126920A4 (en) | 2018-01-03 |
WO2015153727A3 (en) | 2015-11-26 |
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